EP4006355A1 - Laufrad für propellerlüfter, gebläse und ausseneinheit für klimaanlage - Google Patents

Laufrad für propellerlüfter, gebläse und ausseneinheit für klimaanlage Download PDF

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Publication number
EP4006355A1
EP4006355A1 EP19939652.4A EP19939652A EP4006355A1 EP 4006355 A1 EP4006355 A1 EP 4006355A1 EP 19939652 A EP19939652 A EP 19939652A EP 4006355 A1 EP4006355 A1 EP 4006355A1
Authority
EP
European Patent Office
Prior art keywords
upstream
propeller fan
impeller
cylinder
downstream
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
EP19939652.4A
Other languages
English (en)
French (fr)
Other versions
EP4006355A4 (de
Inventor
Soki SAITO
Yoshiki Tabata
Yusuke Fukasawa
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Carrier Japan Corp
Original Assignee
Toshiba Carrier Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Toshiba Carrier Corp filed Critical Toshiba Carrier Corp
Publication of EP4006355A1 publication Critical patent/EP4006355A1/de
Publication of EP4006355A4 publication Critical patent/EP4006355A4/de
Pending legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
    • F04D29/329—Details of the hub
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F04D25/06—Units comprising pumps and their driving means the pump being electrically driven
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F24—HEATING; RANGES; VENTILATING
    • F24F—AIR-CONDITIONING; AIR-HUMIDIFICATION; VENTILATION; USE OF AIR CURRENTS FOR SCREENING
    • F24F1/00—Room units for air-conditioning, e.g. separate or self-contained units or units receiving primary air from a central station
    • F24F1/06—Separate outdoor units, e.g. outdoor unit to be linked to a separate room comprising a compressor and a heat exchanger
    • F24F1/38—Fan details of outdoor units, e.g. bell-mouth shaped inlets or fan mountings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/712—Shape curved concave
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/11—Purpose of the control system to prolong engine life
    • F05D2270/114—Purpose of the control system to prolong engine life by limiting mechanical stresses

Definitions

  • Embodiments of the present invention relate to an impeller for a propeller fan, a blower, and an outdoor unit for an air conditioner.
  • a propeller fan is used as a blower for an outdoor unit of an air conditioner.
  • the propeller fan includes an impeller, and an electric motor that generates the rotational driving force of the impeller.
  • the impeller includes a tubular boss, and a plurality of blades that radially protrude from the outer peripheral surface of the boss.
  • the boss includes: a shaft mounting portion provided with a rotating shaft that connects the electric motor and the propeller fan; a plurality of ribs that radially extend from the outer peripheral surface of the shaft mounting portion to the inner wall of the boss; a downstream-side bridging wall that connects between the plurality of ribs; and an upstream-side bridging wall that connects between the plurality of ribs on the upstream side of the downstream-side bridging wall.
  • the downstream-side bridging wall and the upstream-side bridging wall do not overlap in the direction along the rotation centerline of the propeller fan.
  • the upstream-side bridging wall is provided on the rotation centerline side of the base end portion of the leading edge of each blade.
  • the largest load is generated in the connection portion between the boss and the root portion of the leading edge of each blade.
  • the conventional propeller fan still has room for improving stress concentration in the connection portion between the boss and the root portion of the leading edge of each blade.
  • An object of the present invention is to provide an impeller, which is for a propeller fan, that can more effectively relieve stress concentration in the connection portion between the root portion of the leading edge of each blade and the boss.
  • an aspect of the present invention provides an impeller for a propeller fan including: a boss; and a plurality of blades that radially protrude from an outer peripheral surface of the boss.
  • the boss includes: a cylinder that has the outer peripheral surface and extends from an upstream-side end to a downstream-side end; a plurality of upstream-side bridging walls, each of which has a surface facing a direction along a centerline of the cylinder and a connection portion continuous with the upstream-side end, and extends to inside of the cylinder; and a plurality of downstream-side bridging walls, each of which has a surface facing a direction along the centerline of the cylinder, that is closer to the downstream-side end than the upstream-side bridging walls, and extends to inside of the cylinder.
  • a root portion of a leading edge of each of the plurality of blades is continuous with the upstream-side end.
  • an aspect of the present invention provides a blower including: the propeller fan; and an electric motor that drives the propeller fan.
  • an aspect of the present invention provides an outdoor unit for an air conditioner including: the blower; and a heat exchanger configured to exchange heat with air flowed by the blower.
  • Fig. 1 is a cross-sectional view of an outdoor unit for an air conditioner according to one embodiment of the present invention.
  • the air conditioner includes an outdoor unit 100, and an indoor unit (not shown).
  • the outdoor unit 100 includes: a housing 101; a blower 103 having an electric motor 102; a heat exchanger 105; a compressor 106; a four-way valve (not shown); and a controller (not shown) .
  • the blower 103, the heat exchanger 105, the compressor 106, the four-way valve, and the controller are arranged inside the housing 101.
  • the housing 101 includes: a side plate 111 that covers the side face, a top plate 112 that covers the ceiling; and a bottom plate 113 that covers the bottom face.
  • a partition plate 115 is provided inside the housing 101. The partition plate 115 partitions the inside of the housing 101 into a machine chamber 117 and a heat exchange chamber 118.
  • the side plate 111 has a plurality of inlet holes 111a that suck outside air into the outdoor unit 100.
  • an outlet hole 112a and a bell mouth are provided at the central portion of the top plate 112.
  • the outlet hole 112a exhausts the outside air, which has been sucked into the outdoor unit 100 from the inlet holes 111a of the side plate 111, to the outside of the outdoor unit 100.
  • the compressor 106 is installed on the bottom plate 113 of the machine room 117 and is located below the heat exchanger 105.
  • the heat exchanger 105 is installed in the central portion of the heat exchange chamber 118.
  • the blower 103 is located above the heat exchanger 105 and is installed near the outlet hole 112a of the top plate 112.
  • the outdoor unit 100 is connected to the indoor unit via a refrigerant pipe (not shown).
  • a refrigerant pipe (not shown).
  • the compressor 106 When the refrigeration cycle operation is started, the compressor 106 is driven.
  • the compressor 106 circulates the refrigerant through the refrigerant pipe and leads it to the heat exchanger 105.
  • the operation of the blower 103 is started.
  • the electric motor 102 drives a propeller fan 1 to rotate.
  • the outside air is led to the heat exchange chamber 118 from the inlet holes 111a on the side face of the housing 101, passes through the heat exchanger 105, and exchanges heat with the refrigerant in the heat exchanger 105.
  • the air having been heat-exchanged with the heat exchanger 105 is led to the bell mouth via the blower 103 and is discharged to the outside of the outdoor unit 100 from the outlet hole 112a at the upper portion of the housing 101.
  • Fig. 2 is a perspective view of an impeller for a propeller fan according to the embodiment of the present invention as viewed from the upstream side of the airflow.
  • Fig. 3 is a perspective view of the impeller for the propeller fan according to the embodiment of the present invention as viewed from the downstream side of the airflow.
  • the propeller fan 1 As shown in Fig. 2 and Fig. 3 , the propeller fan 1 according to the present embodiment rotates in the rotation direction R indicated by the solid arrow in Fig. 2 and Fig. 3 so as to cause the fluid, exclusively air, to flow in the flow direction F indicated by the solid arrow in Fig. 2 and Fig. 3 .
  • the propeller fan 1 When the propeller fan 1 is rotated in the direction opposite to the rotation direction R, the fluid flows in the direction opposite to the flow direction F.
  • the propeller fan 1 is applied to, for example, an outdoor unit for an air conditioner, and is used for blowing air to an outdoor heat exchanger.
  • the propeller fan 1 is a so-called axial-flow fan.
  • the propeller fan 1 includes an impeller 2, and an electric motor (not shown) for rotating and driving the impeller 2.
  • the electric motor includes an output shaft (not shown) that transmits rotational driving force to the impeller 2.
  • the output shaft is the rotation center of the impeller 2.
  • Fig. 4 is a longitudinal cross-sectional view of the impeller for the propeller fan according to the embodiment of the present invention.
  • the impeller 2 for the propeller fan 1 is a so-called axial-flow impeller.
  • the impeller 2 is also simply called a propeller.
  • the impeller 2 includes a boss 5 and a plurality of blades 6 that radially protrude from an outer peripheral surface 5a of the boss 5.
  • the impeller 2 is integrally molded with, for example, resin.
  • the plurality of blades 6 are arranged at equal intervals along the outer peripheral surface 5a of the boss 5 in the circumferential direction of the impeller 2, i.e., in the rotation direction R of the propeller fan 1.
  • the impeller 2 has, for example, three blades 6. In this case, the three blades 6 are arranged at every 120° as the central angle.
  • the respective blades 6 are tilted toward the upstream side in the rotation direction of the propeller fan 1, and are arranged on the outer peripheral surface 5a of the boss 5.
  • the root portion 31a of the leading edge 31 of each blade 6 coincides with the upstream-side end 11s of the boss 5.
  • the boss 5 includes: a cylinder 11 that has the outer peripheral surface 5a of the boss 5 and extends from the upstream-side end 11s to the downstream-side end 11b; a plurality of upstream-side bridging walls 12, each of which has a upstream-side end face 12a facing the direction along the centerline of the cylinder 11 and a connection portion 12b continuous with the upstream-side end 11s of the boss 5, and extend to the center of the cylinder 11; a plurality of downstream-side bridging walls 13, each of which has a downstream-side end face 13a facing the direction along the centerline of the cylinder 11 and is closer to the downstream-side end 11b than the upstream-side bridging walls, and extend to the center of the cylinder 11; and a rotating-shaft mounting portion 15 that is disposed in the center of the cylinder 11 via the plurality of upstream-side bridging walls 12 and the plurality of downstream-side bridging walls 13.
  • the rotating-shaft mounting portion 15 is disposed on the rotation centerline of the boss 5 and on the rotation centerline of the impeller 2.
  • the rotating shaft is fixed to the rotating-shaft mounting portion 15.
  • the impeller 2 is connected to the electric motor via the rotating-shaft mounting portion 15 that is fixed to the rotating shaft.
  • the rotating-shaft mounting portion 15 may be one that fixes the inserted rotating shaft or may be one that is integrated with the rotating shaft by insert molding.
  • the plurality of upstream-side bridging walls 12 are a flat plate portion that has substantially uniform-thickness, and extends from the upstream-side end 11s of the cylinder 11 toward the center of the cylinder 11.
  • Each upstream-side bridging wall 12 has: a front end 16 located forward in the rotation direction R of the propeller fan 1; and a rear end 17 located behind the front end 16. The outer edge of each upstream-side bridging wall 12 is continuously connected to the upstream-side end 11s of the cylinder 11.
  • the plurality of downstream-side bridging walls 13 are a flat plate portion that has substantially uniform-thickness, and extends from the downstream-side end 11b of the cylinder 11 toward the center of the cylinder 11.
  • Each downstream-side bridging wall 13 has: a front end 18 located forward in the rotation direction R of the propeller fan 1; and a rear end 19 located behind the front end 18.
  • the outer edge of each downstream-side bridging wall 13 is continuous with the downstream-side end 11b of the cylinder 11.
  • the outer edge of each downstream-side bridging wall 13 may be located inside the cylinder 11 and may not be continuous with the downstream-side end 11b.
  • the plurality of upstream-side bridging walls 12 and the plurality of downstream-side bridging walls 13 are alternately arranged in the rotation direction R of the propeller fan 1.
  • the plurality of upstream-side bridging walls 12 and the plurality of downstream-side bridging walls 13 do not overlap in the direction along the rotation centerline of the propeller fan 1.
  • the number of upstream-side bridging walls 12, the number of downstream-side bridging walls 13, and the number of blades 6 are the same.
  • the upstream-side bridging walls 12, downstream-side bridging walls 13, and blades 6 are regularly arranged around the rotation center of the propeller fan 1.
  • a longitudinal wall 21 extending in the direction of the rotation centerline of the propeller fan 1 is provided.
  • the longitudinal wall 21 has a substantially uniform thickness.
  • a plurality of longitudinal walls 21 are provided. Each of half of the longitudinal walls 21 includes the rear end 17 of each upstream-side bridging wall 12 and the front end 18 of each downstream-side bridging wall 13, while each of the other half of the longitudinal walls 21 includes the front end 16 of each upstream-side bridging wall 12 and the rear end 19 of each downstream-side bridging wall 13.
  • Each longitudinal wall 21 is bridged between the inner peripheral surface 11a of the cylinder 11 and the rotating-shaft mounting portion 15.
  • the plurality of longitudinal walls 21 radially extends from the rotating-shaft mounting portion 15 to the cylinder 11.
  • the upstream-side bridging walls 12 extend in a fan shape from the rotating-shaft mounting portion 15 toward the upstream-side end 11s of the cylinder 11 over the upstream-side ends 21s of the adjacent longitudinal walls 21, the upstream-side end 11s of the cylinder 11, and the upstream-side end 15s of the rotating-shaft mounting portion 15.
  • the rotating-shaft mounting portion 15 corresponds to the pivot of the fan-shaped upstream-side bridging walls 12.
  • the downstream-side bridging walls 13 extend in a fan shape from the downstream-side end 15b of the rotating-shaft mounting portion 15 toward the downstream-side bridging wall of the cylinder 11 over the downstream-side ends 21b of the adjacent longitudinal walls 21, the downstream-side end 11b of the cylinder 11, and the downstream-side end 15b of the rotating-shaft mounting portion 15.
  • the rotating-shaft mounting portion 15 corresponds to the pivot of the fan-shaped downstream-side bridging walls 13. That is, the plurality of upstream-side bridging walls 12 and the plurality of downstream-side bridging walls 13 are alternately and radially arranged around the rotating-shaft mounting portion 15.
  • each upstream-side bridging wall 12 is located behind the root portion 31a of the leading edge 31 of the nearest blade 6 in the rotation direction of the propeller fan 1.
  • the rear end 17 of each upstream-side bridging wall 12 is located behind the root portion 31a of the leading edge 31 of the nearest blade 6.
  • the front end 16 of the connection portion 12b of each upstream-side bridging wall 12 may coincide with the root portion 31a of the leading edge 31 of the nearest blade 6 in the rotation direction of the propeller fan 1, may be located behind the root portion 31a of the leading edge 31 of the nearest blade 6, or may be located in front of the root portion 31a of the leading edge 31 of the nearest blade 6.
  • the front end 16 of each upstream-side bridging wall 12 is located in front of the root portion 31a of the leading edge 31 of the nearest blade 6.
  • the root portion 31a of the leading edge 31 of each blade 6 is preferably sandwiched between the front end 16 and the rear end 17 of the connection portion 12b of the upstream-side bridging wall 12.
  • the front end 16 and the rear end 17 of each upstream-side bridging wall 12 preferably sandwich the root portion 31a of the leading edge 31 of the blade 6.
  • the root portion 31a of the leading edge 31 of each blade 6 is continuous with the upstream-side end 11s of the cylinder 11.
  • the root portion 31a of the leading edge 31 of each blade 6 and the outermost edge of each upstream-side bridging wall 12 face each other with the upstream-side end 11s of the cylinder 11 interposed therebetween, without offsetting in the rotation direction of the propeller fan 1.
  • the impeller 2 includes: the root portion 31a of the leading edge 31 of each blade 6 that is continuous with the upstream-side end 11s of the cylinder 11; and the upstream-side bridging walls 12 that are continuous with the upstream-side end 11s of the cylinder 11. Consequently, the impeller 2 distributes the load to be generated in the root portion 31a of the leading edge 31 of each blade 6 to the upstream-side bridging walls 12, the longitudinal walls 21, and the cylinder 11 of the boss 5 so as to relieve stress concentration in the root portion 31a of the leading edge 31 of each blade 6.
  • the upstream-side end 11s of cylinder 11 is not located between the root portion 31a of the leading edge 31 of each blade 6 and the outermost edge of each upstream-side bridging wall 12, and the upstream-side end 11s of cylinder 11 protrudes toward the upstream-side of the propeller fan 1 to be away from the portion sandwiched between the root portion 31a of the leading edge 31 of each blade 6 and the outermost edge of each upstream-side bridging wall 12, the proportion of the load to be distributed with the upstream-side bridging walls 12 is reduced. That is, the improvement of the stress concentration in the root portion 31a of the leading edge 31 of each blade 6 remains insufficient.
  • the proportion of the load to be distributed with the upstream-side bridging walls 12 is reduced.
  • the proportion of the load to be distributed with the upstream-side bridging walls 12 is reduced. That is, the improvement of the stress concentration in the root portion 31a of the leading edge 31 of each blade 6 remains insufficient.
  • the upstream-side bridging walls 12 bears the load to be generated in the root portion 31a of the leading edge 31 of each blade 6 as intended so as to relieve the stress concentration in the root portion 31a of the leading edge 31 of each blade 6.
  • the reason for such improvement is considered to be that the upstream-side bridging wall 12 in the rear side bears the load to be generated in the root portion 31a located forward via the cylinder 11 in the rotation direction R of the propeller fan 1.
  • each upstream-side bridging wall 12 is located behind the root portion 31a of the leading edge 31 of the nearest blade 6 in the rotation direction R of the propeller fan 1. Consequently, the impeller 2 distributes the load to be generated in the root portion 31a of the leading edge 31 of each blade 6 to the upstream-side bridging walls 12 and the cylinder 11 of the boss 5 so as to relieve the stress concentration in the root portion 31a of the leading edge 31 of each blade 6.
  • the impeller 2 includes the root portion 31a of the leading edge 31 of each blade 6, and this root portion 31a is sandwiched between the front end 16 and the rear end 17 of the upstream-side bridging wall 12. Consequently, the impeller 2 distributes the load to be generated in the root portion 31a of the leading edge 31 of each blade 6 to the upstream-side bridging walls 12 and the cylinder 11 of the boss 5, and thus the impeller 2 more effectively relieves the stress concentration in the root portion 31a of the leading edge 31 of each blade 6.
  • the impeller 2 includes: the upstream-side bridging walls 12; and the downstream-side bridging walls 13, both of which do not overlap in the direction along the rotation centerline of the propeller fan 1. Consequently, the impeller 2 can be readily integrally molded by the mold that can be divided in the direction of the rotation centerline.
  • Fig. 5 is a perspective view of the second aspect of the impeller for the propeller fan according to the embodiment of the present invention as viewed from the upstream side.
  • Fig. 6 is a perspective view of the second aspect of the impeller for the propeller fan according to the embodiment of the present invention as viewed from the downstream side
  • Fig. 7 is a longitudinal cross-sectional view of the second aspect of the impeller for the propeller fan according to the embodiment of the present invention.
  • the impeller 2A of the second aspect for the propeller fan 1 includes a plurality of upstream-side bridging walls 12A that have annularly continuous connection portions 12b located away from the inner peripheral surface 11a of cylinder 11, and are integrated with an annular portion 41.
  • the impeller 2A of the second aspect for the propeller fan 1 is simply referred to as "the impeller 2A".
  • Each upstream-side bridging wall 12A is a plate portion that has a substantially uniform thickness, and is curved in a concave shape from the upstream-side end 11s of the cylinder 11 toward the downstream side.
  • the concave bottom, i.e., the portion of each upstream-side bridging wall 12A farthest from the upstream-side end 11s of the cylinder 11 is closest to the center of the propeller fan 1.
  • the annular portion 41 integrates the plurality of upstream-side bridging walls 12A.
  • the annular portion 41 is a part of the upstream-side bridging walls 12A, and is curved in a concave shape from the upstream-side end 11s of the cylinder 11 toward the downstream side.
  • the portions of the plurality of upstream-side bridging walls 12A near the cylinder 11 are connected to the cylinder 11 for each blade 6, whereas the portions of the plurality of upstream-side bridging walls 12A far from the cylinder 11, that is, the portions of the plurality of upstream-side bridging walls 12A near the rotating-shaft mounting portion 15A are connected in succession by the annular portion 41. That is, the plurality of upstream-side bridging walls 12A are radially arranged from the annular portion 41 disposed inside the cylinder 11 toward the inner peripheral surface 11a of the cylinder 11.
  • the front end 16 of the connection portion 12b of one upstream-side bridging wall 12A is continuous with the rear end 17 of the connection portion 12b of the upstream-side bridging wall 12A located forward in the rotation direction of the propeller fan 1.
  • the front end 16 and the rear end 17 of the adjacent upstream-side bridging walls 12A are connected in succession.
  • These continuous front end 16 and rear end 17 of the upstream-side bridging walls 12A have a rectilinear shape when viewed in the direction of the rotation centerline of the propeller fan 1, and have an arc shape concavely recessed from the upstream-side end 11s of the cylinder 11 toward the downstream side.
  • the longitudinal wall 21A extends in a flat plate shape in the direction of the rotation centerline of the propeller fan 1 connecting these continuous front end 16 and rear end 17.
  • the portion of the cylinder 11 facing the longitudinal wall 21A may be notched as long as it does not interfere with the support of the blades 6. The notch contributes to the weight reduction of the propeller fan 1.
  • the downstream-side bridging walls 13A are provided in the portions surrounded by the upstream-side bridging walls 12A and the cylinder 11 when viewed in the direction of the rotation centerline of the propeller fan 1.
  • An annular longitudinal wall 42 is provided on the inner edge of the annular portion 41.
  • the annular longitudinal wall 42 extends from the inner edge of the annular portion 41 toward the downstream-side end 11b of the cylinder 11.
  • the annular longitudinal wall 42 may or may not reach the downstream-side end 11b of the cylinder 11.
  • the downstream-side end 42b of the annular longitudinal wall 42 is connected to the rotating-shaft mounting portion 15A.
  • the inner edge shape of the annular portion 41 may be a simple circular shape or a polygonal shape as shown in Fig. 5 when viewed in the direction of the rotation centerline of the propeller fan 1.
  • the inner edge shape of the polygon includes: a vertex on a line segment bisecting the connection portion, which is between the upstream-side bridging walls 12A and the cylinder 11, in the rotation direction of the propeller fan 1; and another vertex on a line segment bisecting the arc-shaped portion, which separates the upstream-side bridging walls 12A from the cylinder 11, in the rotation direction of the propeller fan 1.
  • the inner edge shape of the annular portion 41 forms a hexagon.
  • the rotating-shaft mounting portion 15A has a flange 45 that is closer to the downstream-side end 11b of the cylinder 11 than the annular portion 41 shared by the plurality of upstream-side bridging walls 12A.
  • the flange 45 is a wall that extends in the direction perpendicular to the rotation center of the propeller fan 1 and is connected to the downstream-side end 42b of the annular longitudinal wall 42.
  • the flange 45 is a wall that closes the inner boundary of the annular portion 41.
  • the impeller 2A includes: the root portion 31a of the leading edge 31 of each blade 6 that is continuous with the upstream-side end 11s of the cylinder 11; and the upstream-side bridging walls 12A continuous with the upstream-side end 11s of the cylinder 11. Consequently, the impeller 2A distributes the load to be generated in the root portion 31a of the leading edge 31 of each blade 6 to the upstream-side bridging walls 12A and the cylinder 11 of the boss 5 so as to relieves the stress concentration in the root portion 31a of the leading edge 31 of each blade 6.
  • each upstream-side bridging wall 12A is located behind the root portion 31a of the leading edge 31 of the nearest blade 6 in the rotation direction R of the propeller fan 1. Consequently, the impeller 2A distributes the load to be generated in the root portion 31a of the leading edge 31 of each blade 6 to the upstream-side bridging walls 12A and the cylinder 11 of the boss 5 so as to relieve the stress concentration in the root portion 31a of the leading edge 31 of each blade 6.
  • the impeller 2A includes the root portion 31a of the leading edge 31 of each blade 6, and the root portion 31a is sandwiched between the front end 16 and the rear end 17 of the upstream-side bridging wall 12A. Consequently, the impeller 2A distributes the load to be generated in the root portion 31a of the leading edge 31 of each blade 6 to the upstream-side bridging walls 12A and the cylinder 11 of the boss 5, and thus the impeller 2A more effectively relieves the stress concentration in the root portion 31a of the leading edge 31 of each blade 6.
  • the impeller 2A includes: the upstream-side bridging walls 12; and the downstream-side bridging walls 13, both of which do not overlap in the direction along the rotation centerline of the propeller fan 1. Consequently, the impeller 2A can be readily integrally molded by the mold that can be divided in the direction of the rotation centerline.
  • the impeller 2A includes the plurality of upstream-side bridging walls 12A integrated with the annularly continuous annular portion 41 that is located away from the inner peripheral surface 11a of the cylinder 11. Consequently, the impeller 2A distributes the stress to be generated in the root portion 31a of the leading edge 31 of each blade 6 to the upstream-side bridging walls 12A and the cylinder 11 of the boss 5 and also causes the annular portion 41 to bear the stress dispersed by the upstream-side bridging walls 12A, and thus the impeller 2A further relieves the stress concentration in the root portion 31a of the leading edge 31 of each blade 6.
  • Fig. 8 is a view of the boss of the second aspect of the impeller for the propeller fan according to the embodiment of the present invention as viewed from the upstream-side.
  • the impeller 2A for the propeller fan 1 may be provided with drain holes 47, opening width of each of which decreases from the center side to the outer peripheral side of the boss 5, in the upstream-side bridging walls 12A.
  • the drain holes 47 are provided on the outer peripheral portions of the respective upstream-side bridging walls 12A.
  • Each drain hole 47 has an oval shape extending toward the center side of the boss 5 or toward the inner peripheral side of the upstream-side bridging wall 12A.
  • Each drain hole 47 has: a first semi-arc-shaped portion 47a that is provided on the inner peripheral side, and is convex toward the center side of boss 5 or toward the inner peripheral side of the upstream-side bridging wall 12A; and a wedge-shaped portion 47b that is continuous with the chord portion of the first semi-circular arc-shaped portion 47a, and has opening width decreasing at a substantially constant rate from the center side to the outer peripheral side of the boss 5.
  • Each drain hole 47 has a shape that is line-symmetric with respect to an imaginary line extending in the radial direction of the propeller fan 1.
  • the minimum opening width portion of the wedge-shaped portion 47b i.e., the portion closest to the outer edge of the boss 5, is closed in a trapezoidal shape along the outer edge of the boss 5.
  • each drain hole 47 is configured as described above, the impeller 2A can increase the area of the drain holes 47 and appropriately drain moisture such as rainwater to be accumulated in the boss 5 while relieving the stress concentration in the root portion 31a of the leading edge 31 of each blade 6. Since the drain holes 47 are provided in the upstream-side bridging walls 12A that widely spread in the vicinity of the root portions 31a, each drain hole 47 has a degree of freedom to secure a large opening area and can readily drain even water in a solid state, such as a factor of ice or hail. In addition, each drain hole 47 has an egg shape that extends toward the center of the boss 5.
  • the water to be accumulated on the downstream side of the propeller fan 1 is readily drained from the propeller fan 1 along the inclination of the upstream-side bridging walls 12A.
  • the moisture is also readily drained as it travels outwards of the rotating propeller fan 1.
  • Fig. 9 is a perspective view of the third aspect of the impeller for the propeller fan according to the embodiment of the present invention as viewed from the upstream-side.
  • Fig. 10 is a perspective view of the third aspect of the impeller for the propeller fan according to the embodiment of the present invention as viewed from the downstream side.
  • Fig. 11 is a longitudinal cross-sectional view of the third aspect of the impeller for the propeller fan according to the embodiment of the present invention.
  • the impeller 2B of the third aspect for the propeller fan 1 includes a plurality of upstream-side bridging walls 12B that have annularly continuous connection portions 12b located away from the inner peripheral surface 11a of the cylinder 11, and are integrated with an annular portion 41B.
  • the impeller 2B of the third aspect for the propeller fan 1 is simply referred to as "the impeller 2B".
  • Each upstream-side bridging wall 12B is a plate portion that has a substantially uniform thickness and is curved in a concave shape from the upstream-side end 11s of the cylinder 11 toward the downstream side.
  • the concave bottom i.e., the portion of each upstream-side bridging wall 12B farthest from the upstream-side end 11s of the cylinder 11, is closest to the center of the propeller fan 1.
  • the annular portion 41B integrates the plurality of upstream-side bridging walls 12B.
  • the annular portion 41B is a part of the upstream-side bridging walls 12B, and extends from the upstream-side end 11s of the cylinder 11 toward the center of the cylinder 11.
  • the portions of the respective portions of the plurality of upstream-side bridging walls 12B near the cylinder 11 are connected to the cylinder 11 for each blade 6, whereas the portions of the plurality of upstream-side bridging walls 12B far from the cylinder 11, that is, the portions of the plurality of upstream-side bridging walls 12B near the rotating-shaft mounting portion 15B, are connected in succession by the annular portion 41B. That is, the plurality of upstream-side bridging walls 12B are radially arranged from the annular portion 41B disposed inside the cylinder 11 toward the inner peripheral surface 11a of the cylinder 11.
  • the front end 16 of the connection portion 12b of one upstream-side bridging wall 12B is continuous with the rear end 17 of the connection portion 12b of the upstream-side bridging wall 12B located forward in the rotation direction of the propeller fan 1.
  • the front end 16 and the rear end 17 of the adjacent upstream-side bridging walls 12B are connected in succession.
  • These continuous front end 16 and rear end 17 of the upstream-side bridging walls 12B have a curved shape, for example, an arc shape having a center of curvature on the outside of the cylinder 11, i.e., on the side of the blades 6, when viewed in the direction of the rotation centerline of the propeller fan 1.
  • these continuous front end 16 and rear end 17 of the upstream-side bridging walls 12B have an arc shape that is concavely recessed toward the inside of the boss 5. Further, the continuous front end 16 and rear end 17 of the upstream-side bridging walls 12B have an arc shape that is concavely recessed from the upstream-side end 11s of the cylinder 11 toward the downstream side. These continuous front end 16 and rear end 17 are connected to the downstream-side bridging walls 13B via the longitudinal wall 21B. Each longitudinal wall 21B is curved in a concavely recessed arc shape toward the inside of the boss 5 following these continuous front end 16 and rear end 17, and extends with a substantially uniform thickness. As shown in Fig. 10 , of the cylinder 11, the portion facing the longitudinal wall 21B has a notch as long as it does not interfere with the support of the blades 6.
  • the downstream-side bridging walls 13B are provided in the portions surrounded by the upstream-side bridging walls 12B and the cylinder 11 when viewed in the direction of the rotation centerline of the propeller fan 1.
  • the annular longitudinal wall 42 is provided on the inner edge of the annular portion 41B.
  • the annular longitudinal wall 42 extends from the inner edge of the annular portion 41 toward the downstream-side end 11b of the cylinder 11.
  • the annular longitudinal wall 42 may or may not reach the downstream-side end 11b of the cylinder 11.
  • the downstream-side end 42b of the annular longitudinal wall 42 is connected to the rotating-shaft mounting portion 15B.
  • the inner edge shape of the annular portion 41B may be a simple circular shape as shown in Fig. 9 or a polygonal shape when viewed in the direction of the rotation centerline of the propeller fan 1.
  • the inner edge shape of the polygonal shape includes: a vertex on a line segment bisecting the connection portion, which is between the upstream-side bridging walls 12B and the cylinder 11, in the rotation direction of the propeller fan 1; and another vertex on a line segment bisecting the arc-shaped portion, which separates the upstream-side bridging walls 12B from the cylinder 11, in the rotation direction of the propeller fan 1.
  • the rotating-shaft mounting portion 15B has a flange 45 that is closer to the downstream-side end 11b of the cylinder 11 than the annular portion 41B shared by the plurality of upstream-side bridging walls 12B.
  • the flange 45 is a wall that extends in the direction perpendicular to the rotation center of the propeller fan 1 and is connected to the downstream-side end 42b of the annular longitudinal wall 42.
  • the flange 45 is a wall that closes the inner boundary of the annular portion 41.
  • the impeller 2B includes: the root portion 31a of the leading edge 31 of each blade 6 that is continuous with the upstream-side end 11s of the cylinder 11; and the upstream-side bridging walls 12B that are continuous with the upstream-side end 11s of the cylinder 11. Consequently, the impeller 2B distributes the load to be generated in the root portion 31a of the leading edge 31 of each blade 6 to the upstream-side bridging walls 12B and the cylinder 11 of the boss 5 so as to relieve the stress concentration in the root portion 31a of the leading edge 31 of each blade 6.
  • each upstream-side bridging wall 12B is located behind the root portion 31a of the leading edge 31 of the nearest blade 6 in the rotation direction R of the propeller fan 1. Consequently, the impeller 2B distributes the load to be generated in the root portion 31a of the leading edge 31 of each blade 6 to the upstream-side bridging walls 12B and the cylinder 11 of the boss 5 so as to relieve the stress concentration in the root portion 31a of the leading edge 31 of each blade 6.
  • the impeller 2B includes the root portion 31a of the leading edge 31 of each blade 6, and this the root portion 31a is sandwiched between the front end 16 and the rear end 17 of the upstream-side bridging wall 12B. Consequently, the impeller 2B distributes the load to be generated in the root portion 31a of the leading edge 31 of each blade 6 to the upstream-side bridging walls 12B and the cylinder 11 of the boss 5, and thus the impeller 2B more effectively relieves the stress concentration in the root portion 31a of the leading edge 31 of each blade 6.
  • the impeller 2B includes: the upstream-side bridging walls 12B; and the downstream-side bridging walls 13B, both of which do not overlap in the direction along the rotation centerline of the propeller fan 1. Consequently, the impeller 2B can be readily integrally molded by the mold that can be divided in the direction of the rotation centerline.
  • the impeller 2B includes the plurality of upstream-side bridging walls 12B integrated with the annularly continuous annular portion 41B that is located away from the inner peripheral surface 11a of cylinder 11. Consequently, the impeller 2B distributes the stress to be generated in the root portion 31a of the leading edge 31 of each blade 6 to the upstream-side bridging walls 12B and the cylinder 11 of the boss 5 and also causes the annular portion 41 to bear the stress to be dispersed by the upstream-side bridging walls 12B, and thus the impeller 2B further relieves the stress concentration in the root portion 31a of the leading edge 31 of each blade 6.
  • the impeller 2B includes the front end 16 and the rear end 17 of the adjacent upstream-side bridging walls 12B that have an arc shape concavely recessed toward the inside of the boss 5. Consequently, the impeller 2B increases the stress to be borne by the upstream-side bridging walls 12B and the annular portion 41B, and thus the impeller 2B more significantly relieves the stress concentration in the root portion 31a of the leading edge 31 of each blade 6.
  • the impellers 2, 2A, and 2B for the propeller fan 1 according to the present embodiment can more effectively relieve the stress concentration in the connection portion between the boss 5 and the root portion 31a of the leading edge 31 of each blade 6.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Other Air-Conditioning Systems (AREA)
EP19939652.4A 2019-07-31 2019-07-31 Laufrad für propellerlüfter, gebläse und ausseneinheit für klimaanlage Pending EP4006355A4 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/JP2019/029948 WO2021019710A1 (ja) 2019-07-31 2019-07-31 プロペラファンの羽根車、送風機、および空気調和機の室外機

Publications (2)

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EP4006355A1 true EP4006355A1 (de) 2022-06-01
EP4006355A4 EP4006355A4 (de) 2023-04-12

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EP (1) EP4006355A4 (de)
JP (1) JP7245339B2 (de)
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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE112023006619T5 (de) * 2023-07-04 2026-04-23 Mitsubishi Electric Corporation Propellerventilator und klimatisierungsvorrichtung
JP2025171984A (ja) * 2024-05-10 2025-11-20 日本キヤリア株式会社 羽根車

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5870497U (ja) * 1981-11-06 1983-05-13 アイシン精機株式会社 内燃機関用冷却フアン
JPS611897A (ja) * 1984-01-30 1986-01-07 Hitachi Ltd エアコンデイシヨナ用プロペラフアン
JPH05256299A (ja) * 1992-03-13 1993-10-05 Toshiba Corp 送風機
JP3421061B2 (ja) * 1992-08-26 2003-06-30 株式会社日立製作所 プロペラファンおよびこれを備えた空気調和機
JP2005188325A (ja) * 2003-12-24 2005-07-14 Calsonic Kansei Corp モータファンのアンバランス修正構造
JP4388992B1 (ja) * 2008-10-22 2009-12-24 シャープ株式会社 プロペラファン、流体送り装置および成型金型
JP5611277B2 (ja) * 2012-06-20 2014-10-22 三菱電機株式会社 送風機、室外機及び冷凍サイクル装置
WO2014034770A1 (ja) * 2012-08-31 2014-03-06 シャープ株式会社 送風装置
JP2017053301A (ja) * 2015-09-11 2017-03-16 ジョンソンコントロールズ ヒタチ エア コンディショニング テクノロジー（ホンコン）リミテッド プロペラファン及び空気調和機の室外機
JP2019060322A (ja) * 2017-09-28 2019-04-18 日本電産株式会社 軸流ファン

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WO2021019710A1 (ja) 2021-02-04
JPWO2021019710A1 (de) 2021-02-04
CN114207290A (zh) 2022-03-18
JP7245339B2 (ja) 2023-03-23
CN114207290B (zh) 2023-11-10
EP4006355A4 (de) 2023-04-12

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